Front wing for flying machines



.June 24,1930. I 1 H. FocK 1,766,893

FRONT WING FOR FLYING MACHINES Filed Feb. 6, 1928 Patented June 24, 1930 UNITED STATES PATENTpane;g

nmmron FOGKE, or BREMEN, GERMANY, ASSIGNQB' To mama rocks-wanna FLUGZEUGBAU, AKrrEneEsnLLsoHnrn-or Barman. GERMANY FRONT WING FOR FLYING MACHINES Application filed February 6, 1928, Serial No. 252,331, and in Germany lvlarch 12, 19 26. I

It is known that the side steering of flying machines in aeroplane construction may be efiected by pivoting the front wing about an axis of rotation lying approximately in the flying direction. This however gives the disadvantage that the centre of pressure of the front wing tends to be displaced laterally in the direction of the sliding movement which occurs immediately upon the occurrence of a small deviation of the longitudinal axis of the machine from the direction of flight sliding so that a momentum of the front wing about its axis of rotation lying approximately in the flying direction is set up and may rapidly become unmanageably large for the pilot. The front wing therefore rotates further of its own accord and themachine can become quite out of control of the pilot.

The invention has for its object the reduction or elimination of the dangerous transverse momentum of the front wing in that this is given a ne ative dihedral angle or a D a u u I reverse V-posit1o-n, whlch 1S 1n itself known,

- and a negative arrow form (sweep back) which is also in itself known.

With the above and other objects in view, the invention consists in the construction, combination and arrangement of devices hereinafter described and claimed.

In the accompanying drawings Figure l is a plan of an'aeroplane pros vided with a steering wing constructed and arranged in accordance with my invention.

Figure 2 is an elevation of the same.

Figure 3 is a front elevation of the same.

Figure 4: is a diagram illustrating a modification.

Figure 5 is a detail perspective of the same.

Figure 6 is a front diagrammatic detail of the same.

Figure 7 is a diagram showing in plan and front elevation and two cross sections, another modified construction of the steering Wing.

Figure 8 is a diagram showing in plan and front elevation another modified construction of the steering wing.

Referring especially to Figures 1, 2 and 3, the fuselage-is indicated at 1 provided with a rear fixedplane 2. At the front end of the'fuselage' 'is' a steering plane or wing 3 which is pivotally mounted for vertical angular movement, the pivotal axis being indicated at c and substantially coincident with the junction between the wings a, b. p

Upon the occurrence of a sliding angle (course angle) '8 Fig. 1, with a front wing without V and arrow form the centre of pressure would move to the left side of the wing b, thereby 1) tends to lift and a to sink, since the front wing rotates about the axis 0. If negative arrow form is provided in consequence of the course angle the airstream causes uponthe wing portion a a better side ratio and a greater curvature than on the side 7), so that a tends to rise and b to sink. is provided (see Figs. 2 and 3), then the air stream strikes the wing portion a at a greater angle than the portion 7), which also has the effect of lifting a and depressing b.

If moreover invertedV-form By a suitable choice of the V and (b) and arrow form one can reduce the transverse moment of the front wing about the axis 0 to any desired extent. as aero-dynamic investigations have shown.

' The essence of the invention thus resides in that the known transverse inclination of the front wing is combined with the inverted V and arrow form for the purpose of producing a new technical eflect, namely the diminution or elimination of steering momentum y from the transverse inclined movement.

In some cases only a part of the front wing may be given the V and arrow form as shown in Figs. 4.6.

It is also possible-for example with thick Wings to provide only the upper side with invertedV-form, as in Fig. 7 Also, for example with trapezoidal from wings, the front edge may be straight for the purpose of constructive simplicity while the rear edge only presents the reverse arrow form as in Fig. 8. It is essential to the invention that the effective centre-line of the wing presents reverse V and arrow form.

I claim:

1. A flying machine having a front steering plane mounted for vertical angular movement and comprising a pair of oppositely extending wings, the rear edges of which diverge forwardly, the said wings also diverg ing downwardly and the pivotal axis of said steering plane being substantially concident with theline of junction of said wings,

2. A flying machine as claimed'in claim 1, in which only the end portions of the front e ring plan diverg downwardly.-

A y ng ma h ne ascleimed laim in which the upper surfaces of the oppositely extending wings of the front steering plane diverge downwardly, p

In testimony whereof I have hereunto set my hand th 1 d y o S pt mbe HENRICH FQCKE- 

